Sheet entity and an aircraft fuselage with a sheet entity of this type

Patent metadata

Field	Value
Publication number	US-9469084-B2
Application number	US-201113879090-A
Country	US
Kind code	B2
Filing date	Sep 27, 2011
Priority date	Oct 13, 2010
Publication date	Oct 18, 2016
Grant date	Oct 18, 2016

Abstract

A sheet entity, in particular for use as a skin panel for an aircraft fuselage, with a carbon fiber-reinforced plastic laminate and an aluminum-based metal laminate in the edge region, which are connected with one another by means of an adhesive bond, and thereby are electrically insulated from one another, and are stepped back by layers. Also disclosed is a fuselage cell of an aircraft with at least one sheet entity of this type.

First claim

The invention claimed is:

1. A sheet entity with a plastic laminate made from a multiplicity of carbon fibre layers, which are embedded into a plastic matrix, and with a metal-based edge region, wherein the edge region comprises a metal laminate with a multiplicity of aluminum sheets, which are each connected with one another by means of a resin layer accommodating at least one glass fibre layer, wherein the plastic laminate and the metal laminate form an overlap joint based on an electrically insulating adhesive bond comprising an adhesive layer containing at least one glass fibre mat, and in the region of the overlap joint, the plastic laminate and the metal laminate are stepped back by layers,
wherein the metal laminate comprises a non-stepped back foil, as an outermost layer of the metal laminate, extending over and positioned adjacent all edge sections of the stepped back layers of the plastic laminate and the adhesive bond is disposed between and bonds the stepped back carbon fibre layers of the plastic laminate to the metal laminate only at said non-stepped back foil of the metal laminate, such that the stepped back layers of the metal laminate are on a side of the non-stepped back foil that is opposite to the side having said adhesive bond.

2. The sheet entity in accordance with claim 1 , wherein the carbon fibre layers of the plastic laminate are stepped down in the direction of the metal laminate.

3. The sheet entity in accordance with claim 2 , wherein the aluminum sheets and glass fibre layers are stepped down in a direction towards the plastic laminate.

4. The sheet entity in accordance with claim 1 , wherein the plastic laminate and the metal laminate have at least approximately the same wall thickness, and are stepped back such that a wall thickness in the region of the overlap joint corresponds approximately to the wall thickness of one of the plastic laminate and the metal laminate.

5. An aircraft fuselage, with at least one fuselage cell with a multiplicity of skin shells, which are each connected with one another by a longitudinal seam, with one skin shell of a plastic laminate with a multiplicity of carbon fibre layers, which are embedded into a plastic matrix, and with one skin shell of an aluminum laminate with a multiplicity of aluminum sheets, each of which are connected with one another by means of a resin layer accommodating at least one glass fibre layer, wherein the plastic laminate and the aluminum laminate are connected with one another by means of the sheet entity, in accordance with claim 1 .

6. The aircraft fuselage in accordance with claim 5 , wherein the aluminum laminate is a lower shell, the plastic laminate is an upper shell and the sheet entities are side shells, at least in some regions of the fuselage.

7. The aircraft fuselage in accordance with claim 6 , wherein the longitudinal seams of the lower shell, as viewed in the vertical direction of the fuselage cell, are arranged underneath a cabin floor.

8. The sheet entity in accordance with claim 1 , wherein said sheet entity is part of a skin panel of an aircraft fuselage.

Assignees

• Beumler Thomas
• Airbus Operations Gmbh

Inventors

• Beumler Thomas

Classifications

• B29C70/30

  Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core · CPC title

• B64C1/068

  Fuselage sections · CPC title

• B32B2260/023

  Two or more layers · CPC title

• Y02T50/433

  Cross-Sectional Technologies · mapped topic

• B32B2260/046

  Synthetic resin · CPC title